US20050077432A1 - Dual conduction heat dissipating system for a spacecraft - Google Patents
Dual conduction heat dissipating system for a spacecraft Download PDFInfo
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- US20050077432A1 US20050077432A1 US10/885,604 US88560404A US2005077432A1 US 20050077432 A1 US20050077432 A1 US 20050077432A1 US 88560404 A US88560404 A US 88560404A US 2005077432 A1 US2005077432 A1 US 2005077432A1
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- heat
- collectors
- radiating
- receptacle
- walls
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/506—Heat pipes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/503—Radiator panels
Definitions
- the invention relates to the field of spacecraft and more particularly the systems used to dissipate heat produced by certain components (or equipment units) on board such craft.
- each spacecraft must be specifically configured and/or have the RF power of its payload limited.
- dissipation mode described hereinabove imposes a dedicated environment for each traveling wave tube when testing the onboard equipment units.
- An object of the invention is therefore to improve on the above situation.
- the invention proposes a heat dissipating system for a spacecraft comprising amplifier tubes comprising a body extended by a collector, the system comprising a radiating panel installed substantially parallel to the amplifier tubes and thermally coupled to their bodies in such a manner as to radiate to the exterior a portion of the heat that they produce and a radiating receptacle having walls defining a housing adapted to accommodate the collectors of the amplifier tubes and to be thermally coupled to the collectors by at least one of its walls so that heat that they produce is distributed over the wall and between the collectors.
- the amplifier tubes operate at two different conduction temperatures, namely a moderate temperature at the level of the tube bodies and a high temperature at the level of the tube collectors, but distributed and controlled by a radiating receptacle thermally coupled to said collectors.
- the system further comprises at least one heat distributing means adapted to provide the thermal coupling between the collectors and one of the walls of the radiating receptacle and to distribute heat that the collectors produce between the collectors and over the wall.
- the first heat distribution means may be interleaved between the collectors and one of the walls of the radiating receptacle. However, it may equally well be outside the radiating receptacle (and in contact therewith), or integrated into it.
- the receptacle has three walls that define a “radiating trough” preferably of substantially U-shaped cross section.
- a “radiating trough” preferably of substantially U-shaped cross section.
- the second heat distribution means may instead be outside the radiating receptacle (and in contact therewith), or integrated into it.
- each heat distribution means may take the form of at least one thermally conductive material rod, at least one heat pipe or at least one tube in which a heat exchange fluid circulates.
- the receptacle is preferably made from a material chosen for its thermal and mechanical properties, such as aluminum.
- the receptacle is preferably fastened to the collectors directly or indirectly.
- the invention also provides a spacecraft comprising amplifier tubes and at least one heat dissipating system of the type described hereinabove.
- the spacecraft comprises one or more heat dissipating systems provided with radiating receptacles (or rails) that are substantially parallel and, in operation, lie in planes substantially perpendicular to a north-south direction, and/or one or more heat dissipating systems provided with radiating receptacles (or rails) that are substantially parallel and, in operation, lie in planes substantially perpendicular to an east-west direction.
- the invention is particularly well adapted to spacecraft such as satellites, in particular telecommunication satellites, but may also be installed on board remote sensing satellites, space probes, orbiting space stations and spaceships.
- FIG. 1 is a diagram depicting a heat dissipating system according to the invention.
- FIG. 2 is a view in section taken along the line II-II in FIG. 1 .
- FIG. 3 is a diagrammatic side view depicting one embodiment of a portion of a heat dissipating system according to the invention.
- An object of the invention is to dissipate a large part of the heat produced by onboard amplifier tubes of a spacecraft.
- spacecraft means any type of craft or vehicle traveling in space, either in orbit (low or high Earth orbit or geosynchronous orbit) or free of the gravitational field of the Earth, and adapted to transmit signals after amplifying them, and in particular satellites, especially telecommunication or remote sensing satellites, space probes, orbiting space stations and spaceships.
- the spacecraft is a telecommunication satellite.
- a telecommunication satellite comprises amplifier means for amplifying signals to be transmitted before they are transmitted to an Earth station.
- the amplifier means generally take the form of amplifier tubes, such as traveling wave tubes (TWT) T of the type depicted partly and very diagrammatically in FIGS. 1 to 3 .
- TWT traveling wave tubes
- a traveling wave tube T conventionally comprises a body B, of generally parallelepiped shape, for example, connected to a collector C, for example in the shape of a cone or bowl or cylinder, preferably via a thermal decoupling element DT.
- the connection between these three portions of the tube T may be obtained by any means, and in particular by welding, adhesive bonding or nut and bolt fasteners.
- the body B and the collector C are made from materials that are good conductors of heat, as opposed to the thermal decoupler DT, which is a poor conductor of heat to provide some thermal insulation between the body B, operating at a moderate temperature, and the collector C, operating at a high temperature.
- the thermal decoupler DT takes the form of a thermally insulative metal component, for example.
- the tubes of the invention are not equipped with a collector provided with a radiator for radiating heat into space.
- the collectors C of the tubes T are essentially conductive.
- the bodies B of the tubes T are generally parallel to each other and are in thermal contact, for example by way of heat transfer means TC such as one or more heat pipes or heat exchange fluid tubes, with a radiating panel PR, made of aluminum, for example, for radiating into space the heat that it receives.
- the radiating panel PR is designated “north”, “south”, “east”, or “west” according to which plane substantially perpendicular to one of these four directions it is installed in.
- a satellite may comprise a north radiating panel and/or a south radiating panel and/or an east radiating panel and/or a west radiating panel.
- the tubes T thermally coupled to a north or south radiating panel PR are substantially parallel to the east-west direction.
- the satellite is considered to comprise a north (or south) radiating panel substantially perpendicular to east and west lateral panels PL, for example covered with a multilayer insulation (MLI) material.
- MMI multilayer insulation
- the radiating panel PR and the heat transfer means TC form part of a heat dissipating system D according to the invention that also comprises a radiating receptacle RR whose walls (P 1 -P 3 ) define a housing L receiving the collectors C of the amplifier tubes T and which is thermally coupled to the collectors C by at least one of said walls P 1 in order to distribute heat that they produce (and/or receive) between the collectors C and over the wall P 1 .
- the radiating receptacle RR comprises three walls P 1 , P 2 and P 3 that are substantially perpendicular in pairs and define a kind of trough or rail, preferably of substantially U-shaped cross section.
- the radiating receptacle RR is made from the same radiating material as the radiating panel PR, for example.
- the radiating receptacle RR is preferably fastened to the collectors C either directly or indirectly, for example via heat distributing means (RC 1 , RC 2 ) further described hereinafter.
- an insulating strip BI for example an MLI strip
- the radiating receptacle RR is preferably designed to be installed on the satellite so that it has a high space viewing angle, enabling it to dissipate heat efficiently.
- the system D also comprises at least one heat distributing means RC 1 preferably interleaved closely between the collectors C and one of the walls of the radiating receptacle RR and responsible for distributing heat that the collectors C produce (and/or receive) between the various collectors C and over the wall P 1 with which it is in contact.
- at least one heat distributing means RC 1 preferably interleaved closely between the collectors C and one of the walls of the radiating receptacle RR and responsible for distributing heat that the collectors C produce (and/or receive) between the various collectors C and over the wall P 1 with which it is in contact.
- the system D comprises another heat distributing means RC 2 that is preferably closely interleaved between the collectors C and another wall P 3 of the radiating receptacle RR, for distributing the heat that the collectors produce (and/or receive) between the collectors C and over the wall P 3 with which it is in contact.
- another heat distributing means RC 2 that is preferably closely interleaved between the collectors C and another wall P 3 of the radiating receptacle RR, for distributing the heat that the collectors produce (and/or receive) between the collectors C and over the wall P 3 with which it is in contact.
- the two heat distribution means RC 1 and RC 2 take the form of solid rods of a thermally conductive material such as aluminum, for example.
- the heat distribution means RC 1 and RC 2 could take the form of heat transfer systems such as heat pipes or tubes in which a heat exchange fluid circulates.
- a sliding seal intended to limit thermo-elastic forces exerted on the amplifier tube T may also be envisaged.
- a sliding seal of this kind may take the form of films of a thermally conductive material, such as a graphite-based material, for example.
- the system D provides dual conduction, firstly via the radiating panel PR in thermal contact with the body B of the amplifier tubes T and secondly via the radiating receptacle RR in thermal contact with the collectors C of said tubes T, preferably via the heat distributors RC.
- the first conduction therefore takes place at a moderate temperature at the level of the tube bodies and the other at a high temperature at the level of the tube collectors.
- This dual conduction is particularly efficient because the radiating receptacle (or rail) RR is thermally decoupled from the panel PR.
- the invention is concerned generally with any type of spacecraft or space vehicle traveling in space and needing to dissipate heat energy produced by electronic components, such as signal amplifiers, and in particular remote sensing satellites, space probes, orbiting space stations and spaceships.
- the radiating receptacle having a U-shaped section.
- the radiating receptacle may have any shape, and in particular an angle-iron or trough shape.
- the heat distributing means (RC 1 , RC 2 ) are interleaved between the collectors and the walls of the radiating receptacles (or rails).
- the heat distributing means are outside the receptacles, certain walls of the receptacles then having an inside face in contact with the collectors and an outside face in contact with the heat distributing means.
- the heat distributing means increase the radiating area of the collectors and distribute the heat between them via the wall of the radiating receptacle.
- at least one of the walls of the radiating receptacles (or rails) is at least partly hollow (or shaped) to integrate the heat distributing means (RC 1 , RC 2 ).
- the heat transfer means (TC) are interleaved between the bodies of the amplifier tubes and the radiating panel.
- the heat transfer means are above the radiating panel, the latter then having an inside face in contact with the bodies and an outside face in contact with the heat transfer means.
- the radiating panel is at least partly hollow (or conformed) to integrate the heat transfer means (TC).
- the system of the invention is not necessarily fixed. It may be at least partly mobile.
- at least one of the walls of the radiating receptacle (or rail) may be folded during launch (or movement) and deployed during operation. It may also be envisaged that at least one of its walls has an area and/or a geometry that may be varied to control the efficiency of the dissipation system as a function of requirements.
Abstract
Description
- This application is based on French Patent Application No. 03 08 520 filed Nov. 7, 2003, the disclosure of which is hereby incorporated by reference thereto in its entirety, and the priority of which is hereby claimed under 35 U.S.C. §119.
- 1Field of the Invention
- The invention relates to the field of spacecraft and more particularly the systems used to dissipate heat produced by certain components (or equipment units) on board such craft.
- 2. Description of the Prior Art
- The person skilled in the art is well aware that certain spacecraft comprise components such as traveling wave tubes for amplifying signals to be transmitted. Traveling wave tubes produce a large amount of heat which must be dissipated into space. To this end, a first proposal was to use heat transfer systems such as heat pipes or tubes for circulating a heat exchange fluid to couple the bodies of the traveling wave tubes thermally to a radiating panel for radiating the heat into space.
- This proving insufficient, it was then proposed, in particular in U.S. Pat. No. 5,862,462, to couple the body of each traveling wave tube to a collector provided with a high-temperature radiator for radiating heat into space. The radiators being independent of each other, the tubes are virtually independent of each other from a radiating point of view, which is not beneficial in terms of dissipation, environment and mode of operation. This mode of thermal dissipation dissipates into space approximately 50% of the power produced in the saturation mode.
- This is unsatisfactory given the ever increasing power that must be dissipated, which generally goes hand in hand with increasing complexity of the arrangements, especially on the east-west faces of the spacecraft (presence of large antenna reflectors and their support mechanism (hold on release mechanisms—HRMs), large send/receive sources and associated radiators, thruster supports, adjacent collectors, etc.), which significantly reduces the efficiency of radiation into space.
- In other words, because of the insufficient dissipation of heat, and given the technological limitations of its traveling wave tubes, each spacecraft must be specifically configured and/or have the RF power of its payload limited.
- Moreover, the dissipation mode described hereinabove imposes a dedicated environment for each traveling wave tube when testing the onboard equipment units.
- An object of the invention is therefore to improve on the above situation.
- To this end the invention proposes a heat dissipating system for a spacecraft comprising amplifier tubes comprising a body extended by a collector, the system comprising a radiating panel installed substantially parallel to the amplifier tubes and thermally coupled to their bodies in such a manner as to radiate to the exterior a portion of the heat that they produce and a radiating receptacle having walls defining a housing adapted to accommodate the collectors of the amplifier tubes and to be thermally coupled to the collectors by at least one of its walls so that heat that they produce is distributed over the wall and between the collectors.
- Thus the amplifier tubes operate at two different conduction temperatures, namely a moderate temperature at the level of the tube bodies and a high temperature at the level of the tube collectors, but distributed and controlled by a radiating receptacle thermally coupled to said collectors.
- According to another feature of the invention, the system further comprises at least one heat distributing means adapted to provide the thermal coupling between the collectors and one of the walls of the radiating receptacle and to distribute heat that the collectors produce between the collectors and over the wall. For example, the first heat distribution means may be interleaved between the collectors and one of the walls of the radiating receptacle. However, it may equally well be outside the radiating receptacle (and in contact therewith), or integrated into it.
- This significantly improves and homogenizes the distribution of heat between the collectors and the wall.
- In one preferred embodiment, the receptacle has three walls that define a “radiating trough” preferably of substantially U-shaped cross section. In this case, it is advantageous to provide another means of distributing heat, preferably interleaved between the collectors and another of the three walls of the receptacle and adapted to distribute the heat that the collectors produce between the collectors and the other wall. As in the first heat distribution means, the second heat distribution means may instead be outside the radiating receptacle (and in contact therewith), or integrated into it.
- Moreover, each heat distribution means may take the form of at least one thermally conductive material rod, at least one heat pipe or at least one tube in which a heat exchange fluid circulates.
- Furthermore, the receptacle is preferably made from a material chosen for its thermal and mechanical properties, such as aluminum.
- According to another feature of the invention, the receptacle is preferably fastened to the collectors directly or indirectly.
- The invention also provides a spacecraft comprising amplifier tubes and at least one heat dissipating system of the type described hereinabove. For example, the spacecraft comprises one or more heat dissipating systems provided with radiating receptacles (or rails) that are substantially parallel and, in operation, lie in planes substantially perpendicular to a north-south direction, and/or one or more heat dissipating systems provided with radiating receptacles (or rails) that are substantially parallel and, in operation, lie in planes substantially perpendicular to an east-west direction.
- The invention is particularly well adapted to spacecraft such as satellites, in particular telecommunication satellites, but may also be installed on board remote sensing satellites, space probes, orbiting space stations and spaceships.
- Other features and advantages of the invention will become apparent in the light of the following detailed description and the appended drawings.
-
FIG. 1 is a diagram depicting a heat dissipating system according to the invention. -
FIG. 2 is a view in section taken along the line II-II inFIG. 1 . -
FIG. 3 is a diagrammatic side view depicting one embodiment of a portion of a heat dissipating system according to the invention. - The appended drawings constitute part of the description of the invention and may, if necessary, contribute to the definition of the invention.
- An object of the invention is to dissipate a large part of the heat produced by onboard amplifier tubes of a spacecraft.
- In the present context the term “spacecraft” means any type of craft or vehicle traveling in space, either in orbit (low or high Earth orbit or geosynchronous orbit) or free of the gravitational field of the Earth, and adapted to transmit signals after amplifying them, and in particular satellites, especially telecommunication or remote sensing satellites, space probes, orbiting space stations and spaceships.
- Hereinafter, by way of illustrative example, the spacecraft is a telecommunication satellite.
- A telecommunication satellite comprises amplifier means for amplifying signals to be transmitted before they are transmitted to an Earth station. The amplifier means generally take the form of amplifier tubes, such as traveling wave tubes (TWT) T of the type depicted partly and very diagrammatically in FIGS. 1 to 3.
- A traveling wave tube T conventionally comprises a body B, of generally parallelepiped shape, for example, connected to a collector C, for example in the shape of a cone or bowl or cylinder, preferably via a thermal decoupling element DT. The connection between these three portions of the tube T may be obtained by any means, and in particular by welding, adhesive bonding or nut and bolt fasteners.
- The body B and the collector C are made from materials that are good conductors of heat, as opposed to the thermal decoupler DT, which is a poor conductor of heat to provide some thermal insulation between the body B, operating at a moderate temperature, and the collector C, operating at a high temperature. The thermal decoupler DT takes the form of a thermally insulative metal component, for example.
- Unlike the prior art tubes, the tubes of the invention are not equipped with a collector provided with a radiator for radiating heat into space. Here, the collectors C of the tubes T are essentially conductive.
- The bodies B of the tubes T are generally parallel to each other and are in thermal contact, for example by way of heat transfer means TC such as one or more heat pipes or heat exchange fluid tubes, with a radiating panel PR, made of aluminum, for example, for radiating into space the heat that it receives. Depending on the orientation of the satellite, the radiating panel PR is designated “north”, “south”, “east”, or “west” according to which plane substantially perpendicular to one of these four directions it is installed in. For example, a satellite may comprise a north radiating panel and/or a south radiating panel and/or an east radiating panel and/or a west radiating panel.
- For example, the tubes T thermally coupled to a north or south radiating panel PR are substantially parallel to the east-west direction.
- Hereinafter the satellite is considered to comprise a north (or south) radiating panel substantially perpendicular to east and west lateral panels PL, for example covered with a multilayer insulation (MLI) material.
- The radiating panel PR and the heat transfer means TC, where present, form part of a heat dissipating system D according to the invention that also comprises a radiating receptacle RR whose walls (P1-P3) define a housing L receiving the collectors C of the amplifier tubes T and which is thermally coupled to the collectors C by at least one of said walls P1 in order to distribute heat that they produce (and/or receive) between the collectors C and over the wall P1.
- In an example shown in
FIGS. 1 and 3 , the radiating receptacle RR comprises three walls P1, P2 and P3 that are substantially perpendicular in pairs and define a kind of trough or rail, preferably of substantially U-shaped cross section. - The radiating receptacle RR is made from the same radiating material as the radiating panel PR, for example.
- Moreover, the radiating receptacle RR is preferably fastened to the collectors C either directly or indirectly, for example via heat distributing means (RC1, RC2) further described hereinafter.
- Additionally, as shown in
FIG. 3 , it is advantageous to place an insulating strip BI, for example an MLI strip, in the space between the receptacle (or rail) RR and the panel PR. - Also, the radiating receptacle RR is preferably designed to be installed on the satellite so that it has a high space viewing angle, enabling it to dissipate heat efficiently.
- As shown in
FIGS. 1 and 3 , in a preferred embodiment, the system D also comprises at least one heat distributing means RC1 preferably interleaved closely between the collectors C and one of the walls of the radiating receptacle RR and responsible for distributing heat that the collectors C produce (and/or receive) between the various collectors C and over the wall P1 with which it is in contact. - It is even more preferable if the system D comprises another heat distributing means RC2 that is preferably closely interleaved between the collectors C and another wall P3 of the radiating receptacle RR, for distributing the heat that the collectors produce (and/or receive) between the collectors C and over the wall P3 with which it is in contact.
- In the example shown, the two heat distribution means RC1 and RC2 take the form of solid rods of a thermally conductive material such as aluminum, for example. However, the heat distribution means RC1 and RC2 could take the form of heat transfer systems such as heat pipes or tubes in which a heat exchange fluid circulates.
- Placing between the collectors C and each of the heat distributors RCl, RC2 a sliding seal intended to limit thermo-elastic forces exerted on the amplifier tube T may also be envisaged. For example, a sliding seal of this kind may take the form of films of a thermally conductive material, such as a graphite-based material, for example.
- Thanks to the invention, the system D provides dual conduction, firstly via the radiating panel PR in thermal contact with the body B of the amplifier tubes T and secondly via the radiating receptacle RR in thermal contact with the collectors C of said tubes T, preferably via the heat distributors RC. The first conduction therefore takes place at a moderate temperature at the level of the tube bodies and the other at a high temperature at the level of the tube collectors. This dual conduction is particularly efficient because the radiating receptacle (or rail) RR is thermally decoupled from the panel PR.
- Moreover, the distribution of heat in accordance with the invention between the collectors C and the walls P1 -P3 of the radiating receptacle RR:
-
- reduces the temperature of the amplifier tubes T by a few tens of degrees Celsius, typically 30° C. to 40° C., which represents a 30% to 40% increase in the radiated power, enabling the RF power to be increased by approximately 20%,
- averages the thermal cycles over the whole of the heat dissipating system D,
- significantly reduces mechanical fatigue of the amplifier tubes T,
- reduces the constraints on the spacing between the amplifier tubes T,
- simplifies the mechanical/thermal interfaces during testing of the onboard equipment units in the spacecraft, and
- facilitates standardizing the mechanical and thermal interfaces of the tubes.
- The invention is not limited to the embodiments of the heat dissipating system and spacecraft described hereinabove by way of example only, but encompasses all variants within the scope of the following claims that the person skilled in the art may envisage.
- Thus there is described in the foregoing an application of the invention to telecommunication satellites. However, the invention is concerned generally with any type of spacecraft or space vehicle traveling in space and needing to dissipate heat energy produced by electronic components, such as signal amplifiers, and in particular remote sensing satellites, space probes, orbiting space stations and spaceships.
- Moreover, there has been described a radiating receptacle (or rail) having a U-shaped section. However, the radiating receptacle (or rail) may have any shape, and in particular an angle-iron or trough shape.
- Furthermore, there is described in the foregoing an embodiment in which the heat distributing means (RC1, RC2) are interleaved between the collectors and the walls of the radiating receptacles (or rails). However, a variant may be envisaged in which the heat distributing means are outside the receptacles, certain walls of the receptacles then having an inside face in contact with the collectors and an outside face in contact with the heat distributing means. In this case, the heat distributing means increase the radiating area of the collectors and distribute the heat between them via the wall of the radiating receptacle. Another variant may be envisaged in which at least one of the walls of the radiating receptacles (or rails) is at least partly hollow (or shaped) to integrate the heat distributing means (RC1, RC2).
- Similarly, there has been described an embodiment in which the heat transfer means (TC) are interleaved between the bodies of the amplifier tubes and the radiating panel. However, a variant may be envisaged in which the heat transfer means are above the radiating panel, the latter then having an inside face in contact with the bodies and an outside face in contact with the heat transfer means. A further variant may be envisaged in which the radiating panel is at least partly hollow (or conformed) to integrate the heat transfer means (TC).
- Finally, the system of the invention is not necessarily fixed. It may be at least partly mobile. For example, at least one of the walls of the radiating receptacle (or rail) may be folded during launch (or movement) and deployed during operation. It may also be envisaged that at least one of its walls has an area and/or a geometry that may be varied to control the efficiency of the dissipation system as a function of requirements.
Claims (23)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR0308520 | 2003-07-11 | ||
FR0308520A FR2857331B1 (en) | 2003-07-11 | 2003-07-11 | DUAL CONDUCTION HEAT DISSIPATING DEVICE FOR A SPATIAL DEVICE |
Publications (2)
Publication Number | Publication Date |
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US20050077432A1 true US20050077432A1 (en) | 2005-04-14 |
US7048233B2 US7048233B2 (en) | 2006-05-23 |
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US10/885,604 Expired - Fee Related US7048233B2 (en) | 2003-07-11 | 2004-07-08 | Dual conduction heat dissipating system for a spacecraft |
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US (1) | US7048233B2 (en) |
EP (1) | EP1495964B1 (en) |
AT (1) | ATE393094T1 (en) |
DE (1) | DE602004013227T2 (en) |
ES (1) | ES2305683T3 (en) |
FR (1) | FR2857331B1 (en) |
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FR2958449B1 (en) * | 2010-03-30 | 2013-06-14 | Astrium Sas | THERMAL CONTROL DEVICE OF A RADIANT COLLECTOR TUBE |
FR2958448A1 (en) * | 2010-03-30 | 2011-10-07 | Astrium Sas | THERMAL CONTROL DEVICE OF A RADIANT COLLECTOR TUBE HAVING A SCREEN, A FLUID LOOP AND A HIGH TEMPERATURE RADIATOR |
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US9714777B1 (en) | 2014-02-18 | 2017-07-25 | Space Systems/Loral, Llc | Heat pipe and radiator system with thermoelectric cooler |
FR3031969B1 (en) * | 2015-01-27 | 2017-01-27 | Airbus Defence & Space Sas | ARTIFICIAL SATELLITE AND METHOD FOR FILLING A PROPULSIVE GAS TANK OF SAID ARTIFICIAL SATELLITE |
US10118717B2 (en) * | 2015-06-02 | 2018-11-06 | Airbus Defence And Space Sas | Artificial Satellite |
US10932323B2 (en) | 2015-08-03 | 2021-02-23 | Alta Devices, Inc. | Reflector and susceptor assembly for chemical vapor deposition reactor |
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2003
- 2003-07-11 FR FR0308520A patent/FR2857331B1/en not_active Expired - Lifetime
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2004
- 2004-07-05 ES ES04291703T patent/ES2305683T3/en active Active
- 2004-07-05 AT AT04291703T patent/ATE393094T1/en not_active IP Right Cessation
- 2004-07-05 DE DE602004013227T patent/DE602004013227T2/en active Active
- 2004-07-05 EP EP04291703A patent/EP1495964B1/en not_active Not-in-force
- 2004-07-08 US US10/885,604 patent/US7048233B2/en not_active Expired - Fee Related
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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WO2020043562A1 (en) * | 2018-08-29 | 2020-03-05 | Thales Deutschland GmbH Electron Devices | Arrangement of conduction-cooled travelling wave tubes and method for manufacturing an arrangement |
US11854759B2 (en) | 2018-08-29 | 2023-12-26 | Thales Deutschland GmbH Electron Devices | Arrangement of conduction-cooled travelling wave tubes and method for manufacturing an arrangement |
Also Published As
Publication number | Publication date |
---|---|
EP1495964B1 (en) | 2008-04-23 |
EP1495964A1 (en) | 2005-01-12 |
DE602004013227T2 (en) | 2009-05-28 |
US7048233B2 (en) | 2006-05-23 |
FR2857331B1 (en) | 2005-12-02 |
DE602004013227D1 (en) | 2008-06-05 |
FR2857331A1 (en) | 2005-01-14 |
ES2305683T3 (en) | 2008-11-01 |
ATE393094T1 (en) | 2008-05-15 |
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